US 12,104,534 B2
Heat exchanger for aircraft engine
Tatsuya Ueda, Amagasaki (JP); and Sachio Nagamitsu, Amagasaki (JP)
Assigned to Sumitomo Precision Products Co., Ltd., Amagasaki (JP)
Appl. No. 16/977,496
Filed by Sumitomo Precision Products Co., Ltd., Amagasaki (JP)
PCT Filed Mar. 5, 2019, PCT No. PCT/JP2019/008518
§ 371(c)(1), (2) Date Sep. 2, 2020,
PCT Pub. No. WO2019/172221, PCT Pub. Date Sep. 12, 2019.
Claims priority of application No. 2018-038980 (JP), filed on Mar. 5, 2018.
Prior Publication US 2021/0054787 A1, Feb. 25, 2021
Int. Cl. F02C 7/18 (2006.01); F28D 1/03 (2006.01); F28F 3/12 (2006.01)
CPC F02C 7/18 (2013.01) [F28D 1/03 (2013.01); F28F 3/12 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A heat exchanger for an aircraft engine configured to perform heat exchange with an airflow in the aircraft engine, the heat exchanger comprising:
a core allowing a fluid to be cooled to flow therethrough; and
a plurality of plate-shaped radiating fins on a surface of the core; wherein each of the radiating fins includes:
a first portion being formed on the surface of the core and being a flat plate-shaped portion having a generally constant thickness;
a second portion being arranged on a tip side relative to the first portion, having a thickness smaller than that of the first portion, and being a flat plate-shaped portion having a generally constant thickness; and
a connecting portion being connected between the first portion and the second portion, a side portion of the connecting portion being inclined with respect to a side portion of the first portion and a side portion of the second portion; and
the radiating fins are formed such that a ratio y/Y of a height y from the surface of the core to a formation position of the connecting portion to a total height Y of each of the radiating fins from the surface of the core satisfies a relationship of 0.34<y/Y<0.64.